# Boeing Service Bulletin A3514: Revision 1

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2018-0504; AD 2018-19-32 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Service Bulletin A3514](https://openairdocs.org/service-documents/boeing/a3514.md)
- Title as filed: SB-707-00A3514-01--
- Pages: 48
- PDF: https://openairdocs.org/files/sha256/8a/64/8a64985f69d24319e1020557e41eb010dac47ec58cd5c7494ddaef23b1cfefe7
- Page: https://openairdocs.org/service-documents/boeing/a3514/file/8a64985f69d2

## Text

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### Page 1

Commercial 
Airplanes
707
Service Bulletin
ALERT
Number: A3514
Original Issue: July 29, 2004
Revision 1: November 09, 2016
ATA System: 5410
SUBJECT: NACELLES - Nacelle Strut - Front Spar Fitting - Inspection and Replacement
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 300-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 2004 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
Original Issue: July 29, 2004
A3514Revision 1: November 09, 2016
1 of 48
2.0

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Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: July 29, 2004
A3514Revision 1: November 09, 2016
2 of 48
BOEING SERVICE BULLETIN A3514
ALERTALERT
BLANK PAGE

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Table of Contents
Revision Transmittal Sheet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17
D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18
E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20
F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21
H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22
I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22
J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22
1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22
2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 23
K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23
2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . . . 25
3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 26
3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28
FIGURE 1: NACELLE ACCESS - FRONT SPAR FITTING - ALL NACELLES  [Group 1] . . . . . . . . 32
FIGURE 2: NACELLE NUMBER 1 - FRONT SPAR FITTING - INSPECTION . . . . . . . . . . . . . . 33
FIGURE 3: NACELLE NUMBER 2 - FRONT SPAR FITTING - INSPECTION . . . . . . . . . . . . . . 34
FIGURE 4: NACELLE NUMBER 3 - FRONT SPAR FITTING - INSPECTION . . . . . . . . . . . . . . 35
FIGURE 5: NACELLE NUMBER 4 - FRONT SPAR FITTING - INSPECTION . . . . . . . . . . . . . . 36
FIGURE 6: NACELLE NUMBER 1 - FRONT SPAR FITTING AFT LUGS - SURFACE HIGH FREQUENCY
EDDY CURRENT INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37
FIGURE 7: NACELLE NUMBER 2 - FRONT SPAR FITTING AFT LUG - SURFACE HIGH FREQUENCY
EDDY CURRENT INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40
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PROPRIETARY - Copyright © Unpublished
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Original Issue: July 29, 2004
A3514Revision 1: November 09, 2016
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BOEING SERVICE BULLETIN A3514
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FIGURE 8: NACELLE NUMBER 3 - FRONT SPAR FITTING AFT LUG - SURFACE HIGH FREQUENCY
EDDY CURRENT INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43
FIGURE 9: NACELLE NUMBER 4 - FRONT SPAR FITTING AFT LUGS - SURFACE HIGH FREQUENCY
EDDY CURRENT INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: July 29, 2004
A3514Revision 1: November 09, 2016
4 of 48
BOEING SERVICE BULLETIN A3514
ALERTALERT

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Commercial 
Airplanes
707
Service Bulletin
ALERT
Revision Transmittal SheetNumber: A3514Original Issue: July 29, 2004
Revision 1: November 09, 2016
ATA System: 5410
SUBJECT: NACELLES - Nacelle Strut - Front Spar Fitting - Inspection and Replacement
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
Federal Aviation Administration (FAA) Airworthiness Directive AD 2005-08-15 is related to this service bulletin.
The Federal Aviation Administration (FAA) will possibly release an additional Airworthiness Directive related to
this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service
bulletin mandatory.
Effects of this Revision on airplanes on which Original Issue was previously done:
ActionConditionGroup
Do a surface High Frequency Eddy
Current (HFEC) inspection of the aft
lug(s) on the front spar fittings at
nacelle struts, numbers 1, 2, 3 and
4, for any crack. Continue to repeat
the detailed inspection of the front
spar fittings for cracks.
All AirplanesAll
REASON FOR REVISION
This revision is sent to give instructions to do a surface High Frequency Eddy Current (HFEC) inspection of the
aft lug(s) on the front spar fittings.
Terminology defined in Paragraph 3.A., General Information - Notes, only applies to the Accomplishment
Instructions related to surface HFEC inspection of the aft lug(s) on the front spar fittings. Terminology in the
Accomplishment Instructions related to detailed inspection of the front spar fittings has not been changed.
These sections were changed:
1. In Summary, Background, revised the paragraph, updated and added references to Service Related
Problem (SRP) and Fleet Team Digest (FTD).
2. In Summary, Action, revised the paragraph, added instructions for surface HFEC inspection of the aft
lug(s) on the front spar fittings.
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3. In Summary, Compliance, added FAA AD reference and effective date, added paragraph.
4. In Summary, Manpower, deleted the table, added reference to Paragraph 1.G., Manpower.
5. In Summary, Material Information, revised the paragraph.
6. In Summary, revised the summary illustration.
7. In Paragraph 1.A.1., Airplanes, updated the format of the effectivity, removed airplane variable numbers
00003, 00102, 00114, 00154-00156, 00450, 00451, 00602, 05828 and 05829, from this service bulletin
effectivity.
8. In Paragraph 1.C., Reason, revised the paragraph, added references to SRP and FTD, added reason
for revision.
9. In Paragraph 1.D., Description, revised the paragraph, added instructions for surface HFEC inspection
of the aft lug(s) on the front spar fittings, added paragraph to give the effects of this revision on airplanes
on which Original Issue was previously done, added tables for affected maintenance zones.
10. In Paragraph 1.E., Compliance, added FAA AD reference and effective date, added paragraphs, added
Table 2.
11. In Paragraph 1.F., Approval, added Alternative Method of Compliance (AMOC) statement.
12. In Paragraph 1.G., Manpower, added table for surface HFEC inspection of the aft lug(s) on the front
spar fittings.
13. In Paragraph 1.J.1., Existing Data, updated the list of references.
14. Added Paragraph 1.K.2., Damage Tolerance Based Structural Inspections.
15. Added Paragraph 1.M., Software Accomplishment Summary.
16. In Paragraph 2.A., Material - Price and Availability, revised the paragraph.
17. In Paragraph 2.C.2., Parts and Materials Supplied by the Operator, added paragraph.
18. In Paragraph 3.A., General Information, revised the list of notes.
19. In Paragraph 3.B., Work Instructions, added instructions for surface HFEC inspection of the aft lug(s)
on the front spar fittings.
20. In Figure 2 through Figure 5, revised the illustration to show lug hole.
21. Added Figure 6 through Figure 9 for surface HFEC inspection of the aft lug(s) on the front spar fittings.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes,
to show the location of all content changes.
Pages with no vertical lines have no changes.
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REVISION HISTORY
July 29, 2004Original Issue:
November 09, 2016Revision 1:
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A3514Revision 1: November 09, 2016
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PROPRIETARY - Copyright © Unpublished
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Original Issue: July 29, 2004
A3514Revision 1: November 09, 2016
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ALERTALERT
BLANK PAGE

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Commercial 
Airplanes
707
Service Bulletin
ALERT
SummaryNumber: A3514Original Issue: July 29, 2004
Revision 1: November 09, 2016
ATA System: 5410
SUBJECT: NACELLES - Nacelle Strut - Front Spar Fitting - Inspection and Replacement
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN
PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
The inspections shown in this service bulletin will detect cracks in the upper surface and the aft lug(s) of the
front spar fittings on the nacelle struts, numbers 1, 2, 3 and 4. Cracks in the front spar fitting are caused by
fatigue failure originating from fastener holes.
One operator reported cracks in the front spar fitting on nacelle number 4. This airplane had accomplished
Boeing Service Bulletins (SBs) 707-1541 and 707-2958 which provides an inspection and modification to the
front spar fittings. Since the release of SBs 707-1541 and 707-2958 it is believed that the modification and
equivalent production change may not be effective. Operators who have accomplished SBs 707-1541 and
707-2958 are required to do the inspections shown in this service bulletin.
Accomplishment of this service bulletin will detect cracks in the front spar fittings before they become critical.
Any cracked front spar fittings found during the inspections shown in this service bulletin will need to be replaced.
If the work given in this service bulletin is not done, cracks in the front spar fittings of the nacelle struts could
remain undetected. If cracks grow beyond a critical length, the front spar fitting could fail, thus reducing the
structural integrity of the nacelle. This in combination with damage to adjacent attachment structure, could result
in a loss of an engine from the airplane.
This service bulletin is related to SBs 707A3183, 707A3364 and 707A3365, each with similar inspection intervals.
The inboard and outboard nacelle struts are also supported by the more critical midspar fittings which are
inspected and replaced in accordance with SB 707A3183 Revision 6. SB 707A3183 Revision 6 addresses the
fracture of the midspar fitting that resulted in the separation of the inboard strut and engine from the airplane.
SB 707A3183 Revision 6 gives instructions to do detailed inspections and High Frequency Eddy Current (HFEC)
inspections of the midspar fittings. In addition to the midspar fittings, other nacelle fittings require more frequent
inspections to ensure timely detection of cracking which could lead to separation of an engine. Revision 1 of
this service bulletin aligns the HFEC inspection intervals of the front spar fittings with the midspar fittings. SB
707A3364 addresses the diagonal brace tube, end fittings, and mating fittings, and SB 707A3365 addresses
the overwing fitting.
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Boeing Service Related Problem (SRP) 707-SRP-54-0100, 707-SRP-54-0105 and 707-SRP-54-0155 are related
to this service bulletin.
Boeing Fleet Team Digest (FTD) 707 FTD 54-05001 is related to this service bulletin.
ACTION
Detailed Inspection of the Front Spar Fittings at Nacelle Struts, Numbers 1, 2, 3 and 4:
1. Deactivate the leading edge flaps and thrust reversers.
2. Remove and keep access panels or inspection hole caps on each nacelle strut.
3. Do a detailed inspection of the front spar fitting for cracks. If cracks are found, replace the front spar
fitting.
4. Replace the removed access panels or inspection hole caps as applicable.
5. Reactivate the thrust reversers and leading edge flaps.
6. Repeat the detailed inspection at the intervals specified in Paragraph 1.E., Compliance.
Surface High Frequency Eddy Current (HFEC) Inspection of the Aft Lug(s) on the Front Spar Fittings
at Nacelle Struts, Numbers 1, 2, 3 and 4:
1. Deactivate the leading edge flaps and thrust reversers.
2. Remove and keep access panels on each nacelle strut.
3. Remove and keep the bolt from the aft lug(s) on each front spar fitting. Disengage wing-to-spar fitting
from front spar fitting.
4. Do a surface HFEC inspection of the front spar fitting aft lug(s) for any crack. If any crack is found,
replace the front spar fitting.
5. Engage wing-to-spar fitting to front spar fitting. Install the kept bolt in the aft lug(s) on each front spar
fitting.
6. Replace the removed access panels.
7. Reactivate the thrust reversers and leading edge flaps.
8. Repeat the surface HFEC inspection at the intervals specified in Paragraph 1.E., Compliance.
EFFECTIVITY
All 707 and 720 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
COMPLIANCE
Federal Aviation Administration (FAA) Airworthiness Directive AD 2005-08-15 is related to this service bulletin.
The effective date of AD 2005-08-15 is May 31, 2005.
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The Federal Aviation Administration (FAA) will possibly release an additional Airworthiness Directive related to
this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service
bulletin mandatory.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes, inspection and/or repair procedures
given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN A3514
ALERT  ALERT
NACELLE STRUT NUMBER 2 SHOWN,
NACELLE STRUTS NUMBER 1, 3 AND 4 SIMILAR.
DO A SURFACE HFEC
INSPECTION OF THE AFT
LUG(S) FOR ANY CRACK.
TYPICAL CRACK
STRUT CAP SKIN
STRUT CAP SKIN NOT  DO A DETAILED INSPECTION
SHOWN FOR CLARITY  OF THE FRONT SPAR  UP
FITTING FOR CRACKS.
422831
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Commercial 
Airplanes
707
Service Bulletin
ALERT
Number: A3514
Original Issue: July 29, 2004
Revision 1: November 09, 2016
ATA System: 5410
SUBJECT: NACELLES - Nacelle Strut - Front Spar Fitting - Inspection and Replacement
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN
PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is applicable to all 707 and 720 Airplanes, in 2 Groups. The Variable Numbers
and Group Information for the applicable airplanes is given below.
Refer to Service Bulletin Index D6-1647 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP
707-100 Long Body, -100B Long Body, -100B Short Body, -200, -300,
-300B, -300C, -400, 720, and 720B airplanes, line numbers 1 through
917.
-1
707-300C airplanes, line numbers 918 through 1012.-2
Airplane Models:
707-100 LONG BODY, 707-100B LONG BODY, 707-100B SHORT BODY, 707-200, 707-300,
707-300B, 707-300C, 707-400, 720, 720B
GroupVariable Number
1B0001 - B0029
1B0101 - B0125
1B0201 - B0203
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GroupVariable Number
1B0301 - B0306
1B0401 - B0402
1B0501 - B0515
1B2001 - B2008
1B2091 - B2092
1B2101 - B2116
1B2191 - B2194
1B2199
1B2201 - B2227
1B2401 - B2403
1B2501 - B2502
1B2551 - B2553
1B2601 - B2608
100001 - 00002
100004 - 00006
100101
100103 - 00113
100115 - 00153
100201 - 00205
100301 - 00305
100401 - 00449
100471 - 00475
100501 - 00513
100601
100701 - 00703
102001 - 02020
102101 - 02121
102201 - 02207
102301 - 02303
102401 - 02418
104001 - 04005
104020 - 04022
104101 - 04106
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GroupVariable Number
104201 - 04218
104271 - 04272
104301 - 04303
105001 - 05060
105101 - 05138
105201 - 05208
105301 - 05312
105401
105601 - 05605
105631 - 05635
105701 - 05703
105801 - 05802
105821 - 05827
105831 - 05833
105851 - 05854
105891 - 05892
105921 - 05923
105941 - 05942
105961 - 05970
106001 - 06002
106101
106401 - 06404
106451
106461
107001 - 07017
107041 - 07059
107071 - 07081
107101 - 07109
107181
107191
107201 - 07215
107251 - 07271
107401 - 07407
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GroupVariable Number
107451 - 07458
107501 - 07504
107601 - 07626
107661 - 07662
107681 - 07684
107701 - 07702
107801 - 07821
107901 - 07907
108001 - 08008
108021
108051 - 08056
108071 - 08077
108101 - 08104
108121 - 08129
108141 - 08144
108151 - 08153
108171 - 08173
108191 - 08192
108201 - 08210
108221 - 08224
108241 - 08244
108251
108261
108271
108301 - 08320
108324 - 08330
108333
108401 - 08410
108451 - 08452
108471 - 08475
108501 - 08502
108551 - 08553
108581 - 08582
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GroupVariable Number
109001 - 09006
109101 - 09107
109161 - 09165
209166 - 09167
109201 - 09203
209204
109221 - 09223
109227
109231 - 09232
109251
209271
109281
109286 - 09287
209288 - 09290
109411
209421
209438
209441
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
The inspections shown in this service bulletin will detect cracks in the upper surface and the aft lug(s)
of the front spar fittings on the nacelle struts, numbers 1, 2, 3 and 4. Cracks in the front spar fitting are
caused by fatigue failure originating from fastener holes.
One operator reported cracks in the front spar fitting on nacelle number 4. This airplane had
accomplished Boeing Service Bulletins (SBs) 707-1541 and 707-2958 which provides an inspection
and modification to the front spar fittings. Since the release of SBs 707-1541 and 707-2958 it is believed
that the modification and equivalent production change may not be effective. Operators who have
accomplished SBs 707-1541 and 707-2958 are required to do the inspections shown in this service
bulletin.
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Accomplishment of this service bulletin will detect cracks in the front spar fittings before they become
critical. Any cracked front spar fittings found during the inspections shown in this service bulletin will
need to be replaced. If the work given in this service bulletin is not done, cracks in the front spar fittings
of the nacelle struts could remain undetected. If cracks grow beyond a critical length, the front spar
fitting could fail, thus reducing the structural integrity of the nacelle. This in combination with damage
to adjacent attachment structure, could result in a loss of an engine from the airplane.
This service bulletin is related to SBs 707A3183, 707A3364 and 707A3365, each with similar inspection
intervals. The inboard and outboard nacelle struts are also supported by the more critical midspar
fittings which are inspected and replaced in accordance with SB 707A3183 Revision 6. SB 707A3183
Revision 6 addresses the fracture of the midspar fitting that resulted in the separation of the inboard
strut and engine from the airplane. SB 707A3183 Revision 6 gives instructions to do detailed inspections
and High Frequency Eddy Current (HFEC) inspections of the midspar fittings. In addition to the midspar
fittings, other nacelle fittings require more frequent inspections to ensure timely detection of cracking
which could lead to separation of an engine. Revision 1 of this service bulletin aligns the HFEC inspection
intervals of the front spar fittings with the midspar fittings. SB 707A3364 addresses the diagonal brace
tube, end fittings, and mating fittings, and SB 707A3365 addresses the overwing fitting.
Boeing Service Related Problem (SRP) 707-SRP-54-0100, 707-SRP-54-0105 and 707-SRP-54-0155
are related to this service bulletin.
Boeing Fleet Team Digest (FTD) 707 FTD 54-05001 is related to this service bulletin.
Revision 1 is sent to give instructions to do a surface High Frequency Eddy Current (HFEC) inspection
of the aft lug(s) on the front spar fittings.
Terminology defined in Paragraph 3.A., General Information - Notes, only applies to the Accomplishment
Instructions related to surface HFEC inspection of the aft lug(s) on the front spar fittings. Terminology
in the Accomplishment Instructions related to detailed inspection of the front spar fittings has not been
changed.
D. Description
Detailed Inspection of the Front Spar Fittings at Nacelle Struts, Numbers 1, 2, 3 and 4:
1. Deactivate the leading edge flaps and thrust reversers.
2. Remove and keep access panels or inspection hole caps on each nacelle strut.
3. Do a detailed inspection of the front spar fitting for cracks. If cracks are found, replace the front
spar fitting.
4. Replace the removed access panels or inspection hole caps as applicable.
5. Reactivate the thrust reversers and leading edge flaps.
6. Repeat the detailed inspection at the intervals specified in Paragraph 1.E., Compliance.
Surface High Frequency Eddy Current (HFEC) Inspection of the Aft Lug(s) on the Front Spar
Fittings at Nacelle Struts, Numbers 1, 2, 3 and 4:
1. Deactivate the leading edge flaps and thrust reversers.
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2. Remove and keep access panels on each nacelle strut.
3. Remove and keep the bolt from the aft lug(s) on each front spar fitting. Disengage wing-to-spar
fitting from front spar fitting.
4. Do a surface HFEC inspection of the front spar fitting aft lug(s) for any crack. If any crack is found,
replace the front spar fitting.
5. Engage wing-to-spar fitting to front spar fitting. Install the kept bolt in the aft lug(s) on each front
spar fitting.
6. Replace the removed access panels.
7. Reactivate the thrust reversers and leading edge flaps.
8. Repeat the surface HFEC inspection at the intervals specified in Paragraph 1.E., Compliance.
Effects of this Revision on airplanes on which Original Issue was previously done:
ActionConditionGroup
Do a surface High Frequency Eddy
Current (HFEC) inspection of the aft
lug(s) on the front spar fittings at
nacelle struts, numbers 1, 2, 3 and
4, for any crack. Continue to repeat
the detailed inspection of the front
spar fittings for cracks.
All AirplanesAll
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
4-55, 4-56, 4-57, 4-58707-100 LONG BODY, 707-
100B LONG BODY, 707-100B
SHORT BODY, 707-200, 707-
300, 707-300B, 707-300C, 707-
400, 720, 720B
Group 2:
Affected Maintenance Zones
ZoneModel
4-55, 4-56, 4-57, 4-58707-300C
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E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directive AD 2005-08-15 is related to this service
bulletin. The effective date of AD 2005-08-15 is May 31, 2005.
The Federal Aviation Administration (FAA) will possibly release an additional Airworthiness Directive
related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times
given in this service bulletin mandatory.
Accomplish the required actions, based on the applicable conditions in Table 1 and Table 2, in
accordance with Paragraph 3. Accomplishment Instructions.
When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When
more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION
numbers for that CONDITION number or OPTION number.
Table 1: Detailed Inspection of the Front Spar Fittings for cracks at Nacelle Struts, Numbers 1,
2, 3 and 4
Repeat Interval
Not to Exceed
(Flight Hours)
Initial Threshold
(Whichever occurs later)
Action
Time Elapsed Since the
Original Issue Date of
this Service Bulletin
Total Airplane Flight
Hours Since the Original
Airworthiness Certificate
was Granted
700 (b)18 Months3500Detailed Inspec-
tion. Refer to Para-
graph 3.B.
(a)
(a) Replace any cracked fitting prior to further flight.
(b) There is no terminating action at this time.
Table 2: Surface High Frequency Eddy Current (HFEC) Inspection of the Aft Lug(s) on the Front Spar
Fittings for any crack at Nacelle Struts, Numbers 1, 2, 3 and 4
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 1,500 flight cycles or 48
months after the most recent
Detailed Inspection specified in
Table 1, whichever occurs first.
Do PART 2: SURFACE
HFEC INSPECTION OF
THE AFT LUG(S) ON THE
FRONT SPAR FITTINGS
AT NACELLE STRUTS
NUMBERS 1, 2, 3 AND 4
for any crack.
All Airplanes
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Table 2: Surface High Frequency Eddy Current (HFEC) Inspection of the Aft Lug(s) on the Front Spar
Fittings for any crack at Nacelle Struts, Numbers 1, 2, 3 and 4
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before further flight.CONDITION 1 (ACTION
1): Do PART 3: FRONT
SPAR FITTING REPLACE-
MENT.
CONDITION 1: ANY
CRACK FOUND
1,500 flight cycles
or 48 months,
whichever occurs
first.
-CONDITION 1 (ACTION
2): Repeat PART 2: SUR-
FACE HFEC INSPECTION
OF THE AFT LUG(S) ON
THE FRONT SPAR FIT-
TINGS AT NACELLE
STRUTS NUMBERS 1, 2,
3 AND 4 for any crack.
1,500 flight cycles
or 48 months,
whichever occurs
first.
-Repeat PART 2: SUR-
FACE HFEC INSPECTION
OF THE AFT LUG(S) ON
THE FRONT SPAR FIT-
TINGS AT NACELLE
STRUTS NUMBERS 1, 2,
3 AND 4 for any crack.
CONDITION 2: NO
CRACK FOUND
F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable Federal Aviation Regulations (FAR) and are FAA
approved. This service bulletin and the FAA approval were based on the airplane in its original Boeing
delivery configuration or as modified by other FAA approved Boeing changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
In addition, the Manager of the FAA Los Angeles Aircraft Certification Office approves the action (i.e.
inspection or replacement) defined in this service bulletin as an alternative method of compliance to
the requirements of paragraphs (f) and (g) ofAD 2005-08-15. All provisions of AD 2005-08-15 that are
not specifically referenced in the above statement remain fully applicable and must be complied with.
G. Manpower
The tables below show an estimate of the task-hours necessary to do this service bulletin for each
airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with
operator task-hour data if necessary. The estimate does not include lost time. These are some examples
of lost time:
— Time to adjust to the workplace
— Time to schedule the work
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— Time to examine the work
— Time to cure the materials
— Time to make the parts
— Time to find the tools.
Detailed Inspection of the Front Spar Fittings at Nacelle Struts, Numbers 1, 2, 3 and 4
Elapsed HoursTask-HoursNumber of Per-
sons
Task
1.02.02Open Access
1.02.02FIGURE 2
1.02.02FIGURE 3
1.02.02FIGURE 4
1.02.02FIGURE 5
1.02.02Close Access
6.012.0TOTAL FOR EACH AIRPLANE
Surface High Frequency Eddy Current (HFEC) Inspection of the Aft Lug(s) on the Front
Spar Fittings at Nacelle Struts, Numbers 1, 2, 3 and 4
Elapsed HoursTask-HoursNumber of Per-
sons
Task
6.6013.202Open Access
1.201.201FIGURE 6
1.201.201FIGURE 7
1.201.201FIGURE 8
1.201.201FIGURE 9
6.6013.202Close Access
18.0031.20TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Boeing Service Bulletin 707-1541, 707-2958, 707A3183, 707A3364, 707A3365
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b. Boeing Service Related Problem (SRP) 707-SRP-54-0100, 707-SRP-54-0105,
707-SRP-54-0155
c. 707 Maintenance Manual (AMM) Subject 12-2-0, 27-16-202/201, 54-00 Revision Notice (RN)
54-18, 78-5-0/201
d. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2005-08-15
e. Service Bulletin Index D6-1647
f. 707, 720 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00
g. 707 Fleet Team Digest (FTD) 54-05001
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
Life Extension Modification 707/720 Front Spar Chords and Fit-
tings, Inboard and Outboard Struts.
65-80210
Fitting - Front Spar Outboard Nacelle strut, Assy Of.65-13347
Fitting - Front Spar Inboard Nacelle strut, Assy Of.65-42128
Inspection Hole Installation - Nacelle Strut65-58472
These drawings were used to prepare this service bulletin. These drawings are not necessary to
make the specified changes, and are not supplied with this service bulletin. These drawings may
not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
None.
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin affects FCS but no new DTIs are necessary.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
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### Page 25

2.    MATERIAL INFORMATION
A. Material - Price and Availability
The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary for Each
Airplane. As an alternative, operators can purchase the parts from Boeing Spares. This service bulletin
does not show the Boeing price and supply data.
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes, inspection, and/or repair
procedures given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts:
None.
2. Parts and Materials Supplied by the Operator:
The following parts or materials are necessary to do the change in this service bulletin. Parts and
materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine
operator part and material supply to make sure all necessary parts and materials are available.
Group 1:
NotesNameQTYPart Number / Specifica-
tion
(a)Front Spar Fitting - Inboard (Strut num-
bers 2 and 3)
265-42128-1
(a)Front Spar Fitting - Outboard (Strut
numbers 1 and 4)
265-13347-9
(a) Fitting required only if the existing fitting is cracked.
Group 2:
NotesNameQTYPart Number / Specifica-
tion
(a)Front Spar Fitting - Inboard (Strut num-
bers 2 and 3)
265-42128-7
(a)Front Spar Fitting - Outboard (Strut
numbers 1 and 4)
265-13347-9
(a) Fitting required only if the existing fitting is cracked.
3. Parts Modified and Reidentified:
None.
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4. Parts Removed and Not Replaced:
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Obey all of the warnings and cautions given in the specified manual sections.
3. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque Values:
— Values for structural fasteners are given in 707 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 707
Aircraft Maintenance Manual (AMM).
— Values for electrical maintenance tasks are included in Chapter 20 of
Standard Wiring Practices Manual (SWPM).
— Values for engine maintenance tasks are included in Chapter 70 of 707
Aircraft Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
4. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
5. A Detailed Inspection is defined as: An intensive examination of a specific item,
installation, or assembly to detect damage, failure, or irregularity. Available lighting
is normally supplemented with a direct source of good lighting at an intensity deemed
appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be
necessary. Surface cleaning and elaborate procedures may be required.
6. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
7. The instructions in Paragraph 3.B., Work Instructions and the figures can include
operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated
Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing
Index contain data on versions of the tools or test equipment that you can use. It is
permitted to use replaced tools. It is not permitted to use superseded tools.
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8. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
9. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
10. When more than one OPTION is given for a CONDITION, do only one of the OPTION
numbers. When more than one ACTION is given for a CONDITION number or an
OPTION number, do all of the ACTION numbers for that CONDITION number or
OPTION number.
11. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
B. WORK INSTRUCTIONS
Detailed Inspection of the Front Spar Fittings at Nacelle Struts, Numbers 1, 2, 3 and 4
WARNING: MAKE SURE THAT LOCK ASSEMBLY IS PROPERLY INSTALLED TO PREVENT
OPERATION OF LEADING EDGE FLAPS AND SLATS. OPERATION OF SLATS DURING
MAINTENANCE COULD RESULT IN DAMAGE TO THE AIRPLANE OR SERIOUS
INJURY TO MAINTENANCE PERSONNEL.
1. Deactivate the leading edge flaps. Refer to 707 AMM 27-16-202/201.
2. Deactivate all thrust reversers on the left side of the airplane. Refer to 707 AMM 78-5-0/201.
3. Inspect the nacelle strut number 1:
a. Remove access door 1742 on the left side of the strut nearest to the front spar fitting. Refer
to 707 AMM 12-2-0. Or, if the airplane was manufactured with removable inspection hole
caps, as shown in FIGURE 1, remove the inspection hole caps on both sides of the strut
centerline in the crown skin.
b. Do a Detailed Inspection of the upper surface of the front spar fitting as shown in FIGURE 2.
c. If cracks are found during inspection, then remove the cracked front spar fitting and install a
new front spar fitting. Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for fitting
part number.
d. Replace the access door 1742 on the left side of the strut, if removed. Refer to 707 AMM
12-2-0. Or, replace the inspection hole caps.
4. Inspect the nacelle strut number 2:
a. Remove access door 1708 on the left side of the strut nearest to the front spar fitting. Refer
to 707 AMM 12-2-0. Or, if the airplane was manufactured with removable inspection hole
caps, as shown in FIGURE 1, remove the inspection hole caps on both sides of the strut
centerline in the crown skin.
b. Do a Detailed Inspection of the upper surface of the front spar fitting as shown in FIGURE 3.
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c. If cracks are found during inspection, then remove the cracked front spar fitting and install a
new front spar fitting. Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for fitting
part number.
d. Replace the access door 1708 on the left side of the strut, if removed. Refer to 707 AMM
12-2-0. Or, replace the inspection hole caps.
5. Reactivate all thrust reversers on the left side of the airplane. Refer to 707 AMM 78-5-0/201.
6. Deactivate all thrust reversers on the right side of the airplane. Refer to 707 AMM 78-5-0/201.
7. Inspect the nacelle strut number 3:
a. Remove access door 1708 on the left side of the strut nearest to the front spar fitting. Refer
to 707 AMM 12-2-0. Or, if the airplane was manufactured with removable inspection hole
caps, as shown in FIGURE 1, remove the inspection hole caps on both sides of the strut
centerline in the crown skin.
b. Do a Detailed Inspection of the upper surface of the front spar fitting as shown in FIGURE 4.
c. If cracks are found during inspection, then remove the cracked front spar fitting and install a
new front spar fitting. Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for fitting
part number.
d. Replace the access door 1708 on the left side of the strut, if removed. Refer to 707 AMM
12-2-0. Or, replace the inspection hole caps.
8. Inspect the nacelle strut number 4:
a. Remove access door 1742 on the left side of the strut nearest to the front spar fitting. Refer
to 707 AMM 12-2-0. Or, if the airplane was manufactured with removable inspection hole
caps, as shown in FIGURE 1, remove the inspection hole caps on both sides of the strut
centerline in the crown skin.
b. Do a Detailed Inspection of the upper surface of the front spar fitting as shown in FIGURE 5.
c. If cracks are found during inspection, then remove the cracked front spar fitting and install a
new front spar fitting. Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for fitting
part number.
d. Replace the access door 1742 on the left side of the strut, if removed. Refer to 707 AMM
12-2-0. Or, replace the inspection hole caps.
9. Reactivate all thrust reversers on the right side of the airplane. 707 AMM 78-5-0/201.
10. Reactivate the leading edge flaps. Refer to 707 AMM 27-16-202/201.
11. Put the airplane back to a serviceable condition.
Surface High Frequency Eddy Current (HFEC) Inspection of the Aft Lug(s) on the Front Spar
Fittings at Nacelle Struts, Numbers 1, 2, 3 and 4:
1. Do PART 1: OPEN ACCESS.
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2. Do PART 2: SURFACE HFEC INSPECTION OF THE AFT LUG(S) ON THE FRONT SPAR
FITTINGS AT NACELLE STRUTS NUMBERS 1, 2, 3 AND 4 for any crack.
a. CONDITION 1: ANY CRACK FOUND
(1) CONDITION 1 (ACTION 1): Do PART 3: FRONT SPAR FITTING REPLACEMENT.
(2) CONDITION 1 (ACTION 2): Repeat PART 2: SURFACE HFEC INSPECTION OF THE
AFT LUG(S) ON THE FRONT SPAR FITTINGS AT NACELLE STRUTS NUMBERS 1,
2, 3 AND 4 for any crack at the repeat interval specified in Paragraph 1.E., Compliance.
b. CONDITION 2: NO CRACK FOUND
(1) Repeat PART 2: SURFACE HFEC INSPECTION OF THE AFT LUG(S) ON THE FRONT
SPAR FITTINGS AT NACELLE STRUTS NUMBERS 1, 2, 3 AND 4 for any crack at the
repeat interval specified in Paragraph 1.E., Compliance.
3. Do PART 4: CLOSE ACCESS.
4. Put the airplane back to a serviceable condition.
PART 1: OPEN ACCESS
WARNING: MAKE SURE THAT LOCK ASSEMBLY IS PROPERLY INSTALLED TO PREVENT
OPERATION OF LEADING EDGE FLAPS AND SLATS. OPERATION OF SLATS DURING
MAINTENANCE COULD RESULT IN DAMAGE TO THE AIRPLANE OR SERIOUS
INJURY TO MAINTENANCE PERSONNEL.
1. Deactivate the leading edge flaps. Refer to 707 AMM 27-16-202/201 as an accepted procedure.
2. Deactivate all thrust reversers. Refer to 707 AMM 78-5-0/201 as an accepted procedure.
3. Remove and keep the access panels shown in the table below. Refer to 707 AMM 12-2-0 for
access panel location.
Access Panel NumberNacelle Strut Number
1745, 17531
1709, 17212
1709, 17213
1745, 17534
4. At nacelle struts number 1, 2, 3 and 4, remove and keep the bolt from the aft lug(s) on each front
spar fitting. Disengage wing-to-spar fitting from front spar fitting. Refer to 707 AMM 54-00, Revision
Notice (RN) 54-18 as an accepted procedure.
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PART 2: SURFACE HFEC INSPECTION OF THE AFT LUG(S) ON THE FRONT SPAR FITTINGS
AT NACELLE STRUTS NUMBERS 1, 2, 3 AND 4
1. Do a magnetic inspection of the front spar fitting to find if the material is aluminum or steel, and
do a surface High Frequency Eddy Current (HFEC) inspection of the front spar fitting aft lug(s) for
any crack, in accordance with the figures below:
FigureNacelle Strut Number
FIGURE 61
FIGURE 72
FIGURE 83
FIGURE 94
PART 3: FRONT SPAR FITTING REPLACEMENT
1. Contact The Boeing Company for instructions to do the actions that follow, and do the instructions:
a. Remove the cracked front spar fitting.
b. Install a new front spar fitting. Refer to Paragraph 2.C., Parts Necessary for Each Airplane,
for fitting part number.
PART 4: CLOSE ACCESS
1. At nacelle struts number 1, 2, 3 and 4, engage wing-to-spar fitting to front spar fitting. Install the
kept bolt in the aft lug(s) on each front spar fitting. Refer to 707 AMM 54-00, RN 54-18 as an
accepted procedure.
2. Install the kept access panels shown in the table below. Refer to 707 AMM 12-2-0 for access panel
location.
Access Panel NumberNacelle Strut Number
1745, 17531
1709, 17212
1709, 17213
1745, 17534
3. Reactivate all thrust reversers. Refer to 707 AMM 78-5-0/201 as an accepted procedure.
4. Reactivate the leading edge flaps. Refer to 707 AMM 27-16-202/201 as an accepted procedure.
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### Page 32 (OCR)

BOEING SERVICE BULLETIN А3514
ALERT  ALERT
This Figure applies only to: Group 1.
INSPECTION
HOLE CAPS
UP
ACCESS  FWD <
PANEL
FIGURE 1: NACELLE ACCESS - FRONT SPAR FITTING - ALL NACELLES
(SHEET 1 OF 1)
Original Issue: July 29, 2004
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Work - See page 1 for details.  32 of 48

### Page 33

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
MORE DATAREFERENCESPROCEDURENAMETASKSTEP
(a)-Detailed InspectionFront Spar FittingInspect1
(a) Do a detailed inspection of the upper surface of the front spar fitting. Pay particular attention to the front
spar fitting surface around the fasteners.
FIGURE 2: NACELLE NUMBER 1 - FRONT SPAR FITTING - INSPECTION
(SHEET 1 OF 1)
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### Page 34

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
MORE DATAREFERENCESPROCEDURENAMETASKSTEP
(a)-Detailed InspectionFront Spar FittingInspect1
(a) Do a detailed inspection of the upper surface of the front spar fitting. Pay particular attention to the front
spar fitting surface around the fasteners.
FIGURE 3: NACELLE NUMBER 2 - FRONT SPAR FITTING - INSPECTION
(SHEET 1 OF 1)
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### Page 35

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
MORE DATAREFERENCESPROCEDURENAMETASKSTEP
(a)-Detailed InspectionFront Spar FittingInspect1
(a) Do a detailed inspection of the upper surface of the front spar fitting. Pay particular attention to the front
spar fitting surface around the fasteners.
FIGURE 4: NACELLE NUMBER 3 - FRONT SPAR FITTING - INSPECTION
(SHEET 1 OF 1)
Export Controlled ECCN: 9E991 - BOEING
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Original Issue: July 29, 2004
A3514Revision 1 November 09, 2016
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BOEING SERVICE BULLETIN A3514
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### Page 36

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
MORE DATAREFERENCESPROCEDURENAMETASKSTEP
(a)-Detailed InspectionFront Spar FittingInspect1
(a) Do a detailed inspection of the upper surface of the front spar fitting. Pay particular attention to the front
spar fitting surface around the fasteners.
FIGURE 5: NACELLE NUMBER 4 - FRONT SPAR FITTING - INSPECTION
(SHEET 1 OF 1)
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### Page 37

FIGURE 6: NACELLE NUMBER 1 - FRONT SPAR FITTING AFT LUGS - SURFACE HIGH FREQUENCY
EDDY CURRENT INSPECTION
(SHEET 1 OF 3)
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### Page 38

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)1-Front Spar FittingInspect1
(b) (c)2-Front Spar Fitting Aft
Lug
Inspect2
(a) Do a magnetic inspection of the front spar fitting to find if the material is aluminum or steel. Use a magnet
to find if there is a magnetic force that pulls the magnet to the front spar fitting. If there is a magnetic force,
the front spar fitting is made from steel. If there is no magnetic force, the front spar fitting is made from
aluminum.
(b) For aluminum front spar fitting, do a surface HFEC inspection around the lug hole on the two sides of
each aft lug of the front spar fitting for any crack in accordance with 707, 720 NDT Manual Part 6, 51-00-
00, Figure 4 or Figure 23.
FIGURE 6: NACELLE NUMBER 1 - FRONT SPAR FITTING AFT LUGS - SURFACE HIGH FREQUENCY
EDDY CURRENT INSPECTION
(SHEET 2 OF 3)
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### Page 39

More DataQtyIdentificationNameTaskStep
(c) For steel front spar fitting, do a surface HFEC inspection around the lug hole on the two sides of each aft
lug of the front spar fitting for any crack in accordance with 707, 720 NDT Manual Part 6, 51-00-00, Figure
13 or Figure 24.
FIGURE 6: NACELLE NUMBER 1 - FRONT SPAR FITTING AFT LUGS - SURFACE HIGH FREQUENCY
EDDY CURRENT INSPECTION
(SHEET 3 OF 3)
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### Page 40

FIGURE 7: NACELLE NUMBER 2 - FRONT SPAR FITTING AFT LUG - SURFACE HIGH FREQUENCY EDDY
CURRENT INSPECTION
(SHEET 1 OF 3)
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A3514Revision 1 November 09, 2016
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ALERTALERT

### Page 41

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)1-Front Spar FittingInspect1
(b) (c)1-Front Spar Fitting Aft
Lug
Inspect2
(a) Do a magnetic inspection of the front spar fitting to find if the material is aluminum or steel. Use a magnet
to find if there is a magnetic force that pulls the magnet to the front spar fitting. If there is a magnetic force,
the front spar fitting is made from steel. If there is no magnetic force, the front spar fitting is made from
aluminum.
(b) For aluminum front spar fitting, do a surface HFEC inspection around the lug hole on the two sides of the
aft lug of the front spar fitting for any crack in accordance with 707, 720 NDT Manual Part 6, 51-00-00,
Figure 4 or Figure 23.
FIGURE 7: NACELLE NUMBER 2 - FRONT SPAR FITTING AFT LUG - SURFACE HIGH FREQUENCY EDDY
CURRENT INSPECTION
(SHEET 2 OF 3)
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### Page 42

More DataQtyIdentificationNameTaskStep
(c) For steel front spar fitting, do a surface HFEC inspection around the lug hole on the two sides of the aft
lug of the front spar fitting for any crack in accordance with 707, 720 NDT Manual Part 6, 51-00-00, Figure
13 or Figure 24.
FIGURE 7: NACELLE NUMBER 2 - FRONT SPAR FITTING AFT LUG - SURFACE HIGH FREQUENCY EDDY
CURRENT INSPECTION
(SHEET 3 OF 3)
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### Page 43

FIGURE 8: NACELLE NUMBER 3 - FRONT SPAR FITTING AFT LUG - SURFACE HIGH FREQUENCY EDDY
CURRENT INSPECTION
(SHEET 1 OF 3)
Export Controlled ECCN: 9E991 - BOEING
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A3514Revision 1 November 09, 2016
43 of 48
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ALERTALERT

### Page 44

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)1-Front Spar FittingInspect1
(b) (c)1-Front Spar Fitting Aft
Lug
Inspect2
(a) Do a magnetic inspection of the front spar fitting to find if the material is aluminum or steel. Use a magnet
to find if there is a magnetic force that pulls the magnet to the front spar fitting. If there is a magnetic force,
the front spar fitting is made from steel. If there is no magnetic force, the front spar fitting is made from
aluminum.
(b) For aluminum front spar fitting, do a surface HFEC inspection around the lug hole on the two sides of the
aft lug of the front spar fitting for any crack in accordance with 707, 720 NDT Manual Part 6, 51-00-00,
Figure 4 or Figure 23.
FIGURE 8: NACELLE NUMBER 3 - FRONT SPAR FITTING AFT LUG - SURFACE HIGH FREQUENCY EDDY
CURRENT INSPECTION
(SHEET 2 OF 3)
Export Controlled ECCN: 9E991 - BOEING
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ALERTALERT

### Page 45

More DataQtyIdentificationNameTaskStep
(c) For steel front spar fitting, do a surface HFEC inspection around the lug hole on the two sides of the aft
lug of the front spar fitting for any crack in accordance with 707, 720 NDT Manual Part 6, 51-00-00, Figure
13 or Figure 24.
FIGURE 8: NACELLE NUMBER 3 - FRONT SPAR FITTING AFT LUG - SURFACE HIGH FREQUENCY EDDY
CURRENT INSPECTION
(SHEET 3 OF 3)
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### Page 46

FIGURE 9: NACELLE NUMBER 4 - FRONT SPAR FITTING AFT LUGS - SURFACE HIGH FREQUENCY
EDDY CURRENT INSPECTION
(SHEET 1 OF 3)
Export Controlled ECCN: 9E991 - BOEING
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Work - See page 1 for details.
Original Issue: July 29, 2004
A3514Revision 1 November 09, 2016
46 of 48
BOEING SERVICE BULLETIN A3514
ALERTALERT

### Page 47

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)1-Front Spar FittingInspect1
(b) (c)2-Front Spar Fitting Aft
Lug
Inspect2
(a) Do a magnetic inspection of the front spar fitting to find if the material is aluminum or steel. Use a magnet
to find if there is a magnetic force that pulls the magnet to the front spar fitting. If there is a magnetic force,
the front spar fitting is made from steel. If there is no magnetic force, the front spar fitting is made from
aluminum.
(b) For aluminum front spar fitting, do a surface HFEC inspection around the lug hole on the two sides of
each aft lug of the front spar fitting for any crack in accordance with 707, 720 NDT Manual Part 6, 51-00-
00, Figure 4 or Figure 23.
FIGURE 9: NACELLE NUMBER 4 - FRONT SPAR FITTING AFT LUGS - SURFACE HIGH FREQUENCY
EDDY CURRENT INSPECTION
(SHEET 2 OF 3)
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ALERTALERT

### Page 48

More DataQtyIdentificationNameTaskStep
(c) For steel front spar fitting, do a surface HFEC inspection around the lug hole on the two sides of each aft
lug of the front spar fitting for any crack in accordance with 707, 720 NDT Manual Part 6, 51-00-00, Figure
13 or Figure 24.
FIGURE 9: NACELLE NUMBER 4 - FRONT SPAR FITTING AFT LUGS - SURFACE HIGH FREQUENCY
EDDY CURRENT INSPECTION
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
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Original Issue: July 29, 2004
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ALERTALERT

---
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